DOCSLIB.ORG

Deploying 87 Satellites in One Launch: Design Trades Completed for the 2015 SHERPA Flight Hardware

Total Page：16

File Type：pdf, Size：1020Kb

Download full-text PDF Read full-text
Deploying 87 Satellites in One Launch: Design Trades Completed for the 2015 SHERPA Flight Hardware SSC15-II-2 Deploying 87 Satellites in One Launch: Design trades completed for the 2015 SHERPA flight hardware Kaitlyn Kelley, Mitch Elson, Jason Andrews Spaceflight Services 3415 S 116th St #123, Tukwila, WA 98168; (801) 618-7223 [email protected] ABSTRACT Launch remains an obstacle for small satellites, which are often limited to small platforms, aft bulkheads, and accommodations for a single P-Pod. While launch vehicles have expanded the space available to small satellites, the largest number of satellites deployed in a single launch stands at thirty-seven. Spaceflight has secured a single launch opportunity in 2015 for no less than 87 small satellites. The ability to support so many satellites stems from tactical design decisions. This paper focuses on the design trades for the payload adapters developed for the 2015 SHERPA launch. Three unique payload adapters were designed to interface to the Moog ESPA Grande ring, the core of the SHERPA spacecraft. Each is an aluminum plate that interfaces to the 24” bolt-hole pattern on the five ESPA Grande ports. For these adapters, a balance was struck between designing to the unique payload in the flight configuration and developing a reusable system. The paper discusses the initial design trades regarding the adapter plate capabilities and how these trades have affected the plates’ utility on later SHERPA missions. INTRODUCTION capacity for adapter equipment and offer more options Spaceflight Services is poised to break the record for for creative integration. With this additional volume the most satellites launched on a single launch vehicle, and capacity, the record number of satellites in a single doubling the number previously launched. launch is primed to be broken. As more small satellites clamor for launch, many 2015 SHERPA MISSION organizations have begun filling excess capacity with The 2015 SHERPA mission addresses the limitations of small satellites and nanosatellites. Innovative Solutions current launch configurations by maximizing the in Space B.V. and Tyvak Nanosatellite Systems have number of payloads integrated to the structure. It is an been launching nanosatellites as secondary payloads for ESPA Grande-derived satellite deployment system years. Nanosatellite deployment has even begun from intended for launch on any Evolved Expendable the International Space Station, through the commercial Launch Vehicle (EELV). The SHERPA is a free‐flier company NanoRacks. auxiliary payload deployment system capable of NASA and the U.S. government also launched large deploying up to 1500 kg. Secondary payloads are numbers of small satellites in the past. The integrated to each port of the SHERPA and the primary Operationally Responsive Space office recently payload can be safely integrated to the top of SHERPA. launched 29 CubeSats on a Minotaur launch vehicle. Flight Configuration Roscosmos, a Russian agency, develops cluster missions around a few main payloads and fills the While the high number of satellites on this mission is in remaining space with small satellites and nanosatellites. part due to CubeSat constellations, the SHERPA concept is well suited to support small spacecraft that There is an upward trend in the number of satellites range from CubeSats to 300kg. By developing unique deployed during each launch. Moving from one adapters for the standard ports, Spaceflight has enabled satellite to nearly forty is a huge advance. Spaceflight many different sizes of spacecraft to deploy from Services is poised to take the next leap; from forty to SHERPA, including the DARPA eXCITe nearly ninety satellites deployed in a single launch. microsatellite, built by NovaWurks, and two BlackSky Unlike the other commercial companies mentioned, Global Pathfinder satellites. Future planned which focus primarily on CubeSats, Spaceflight configurations involve multiple SHERPA rings on a integrates microsatellites as well. This ability opens up single launch as well as support for much larger new opportunities for small satellite integration on spacecraft on the forward section of the SHERPA ring. larger vehicles. These larger launch vehicles have more Kelley 1 29th Annual AIAA/USU Conference on Small Satellites For the 2015 SHERPA mission the final configuration For microsatellite deployments, Spaceflight has incorporates three microsatellites and 84 CubeSats of selected the Planetary Systems Corporations Motorized which the majority are 3Us. The microsatellites LightBand as our preferred separation system. represent two different spectrums with regard to mass Planetary Systems has developed and published and interfaces. This demonstrates the capabilities of standards for mechanical and electrical interfaces. using the modular approach Spaceflight took in the Spaceflight offers our services at fixed prices, so known design and implementation of its adapter hardware. technical specifications and cost allow Spaceflight to have a high degree of confidence in its pricing. With extensive flight heritage, the Motorized LightBands provides confidence in its mission assurance. That is further enhanced by the amount of testing that Planetary Systems has completed. The company provides the related data in their published documentation. Finally, the Motorized LightBands have compiled a great deal of data on their deployment characteristics based on their extensive flight heritage. This supports another part of overall mission assurance, and provides the customer with the knowledge that their spacecraft will have minimal tip-off rates. This is an important factor in our post-deployment system stabilization and allows Spaceflight to deploy spacecraft as soon as possible after launch. Figure 1: 2015 SHERPA Flight Configuration In addition to the microsatellites, there are 84 CubeSats One of the innovative microsatellites included on the manifested on the 2015 SHERPA. Spaceflight chose to manifest is a 160kg system, developed and flown by use the QuadPack, a CubeSat deployment system NovaWurks. Based on our current customer inputs, this procured from Innovative Solution in Space of the 125kg to 250kg spacecraft class will be an area of high Netherlands, to deploy the CubeSats. The “Quad” in demand. Spaceflight has concluded that this is one of QuadPack refers to the baseline configuration to the worst served markets in terms of access to space. support four 3U CubeSats. This can be configured to Historically, this category was served by foreign launch support any number of CubeSats that can be divided service providers and the U.S. Government. As into that space. For the 2015 SHERPA mission technology advances, this class of spacecraft has begun Spaceflight is utilizing the modularity to fly a number to catch the interest of commercial satellite providers. of 6U CubeSats. This new group of customers does not have access to the Government small launch vehicles, and, to date, Not only do the QuadPacks provide modularity in the commercial small launch vehicles are too expensive for CubeSat configuration, the ability to integrate the the secondary market. While there are efforts underway system through multiple bolt hole patterns enables to develop lower cost commercial small launch additional integration options. Spaceflight has designed vehicles, the efficiencies in cost provided by the an adapter plate that integrates the aft end to the plate. SHERPA concept will remain a competitive means to This design allows Spaceflight to place seven access popular orbits. QuadPacks per SHERPA port. Two microsatellites on the 2015 SHERPA mission The QuadPacks are compatible with CubeSats support the early phases of a constellation build out. developed to the Cal Poly CubeSat Standards. This With numerous spacecraft manifested on this mission system also offers options to support some of the Spaceflight has had to consider not only the mass to emerging trends in the CubeSat world; such as “tuna orbit, but also the volume consumed by any given can” extrusion, and volumegrowth around the rail spacecraft. By developing an adapter system that system. places two spacecraft on a single port, Spaceflight is able to maintain its Internet advertised pricing. Mission Concept of Operations Customers can recognize the benefit of this pricing by A significant driver for the requirements of the 2015 designing to industry and SHERPA published SHERPA mission is the overriding concept of avoiding standards. This will increase the number of rideshare any additional risk to the primary spacecraft or the opportunities available and keep the cost per kg low. launch vehicle. Secondary payload mechanical and Kelley 2 29th Annual AIAA/USU Conference on Small Satellites electrical designs have been addressed over the years at • 45 minute payload deployment time the Small Satellite Conference; therefore it will not be discussed in this paper. • Continue to relay telemetry over selected ground sites until end of battery life The SHERPA is to be separated from the launch approximately 10 hours post SHERPA vehicle prior to any deployments. This operation separation. enables Spaceflight to minimize the risk to the launch service provider because it is responsible for all deployments after SHERPA separation. This separation requirement drove Spaceflight to develop a robust avionics system at a competitive price. The avionics system had to be compatible with Spaceflight’s advertised launch pricing. In the end, we determined that developing our own system was the best solution. The avionics incorporated into the 2015 SHERPA mission
Load more

Recommended publications
  • Spacex Launch Manifest - a List of Upcoming Missions 25 Spacex Facilities 27 Dragon Overview 29 Falcon 9 Overview 31 45Th Space Wing Fact Sheet
    COTS 2 Mission Press Kit SpaceX/NASA Launch and Mission to Space Station CONTENTS 3 Mission Highlights 4 Mission Overview 6 Dragon Recovery Operations 7 Mission Objectives 9 Mission Timeline 11 Dragon Cargo Manifest 13 NASA Slides – Mission Profile, Rendezvous, Maneuvers, Re-Entry and Recovery 15 Overview of the International Space Station 17 Overview of NASA’s COTS Program 19 SpaceX Company Overview 21 SpaceX Leadership – Musk & Shotwell Bios 23 SpaceX Launch Manifest - A list of upcoming missions 25 SpaceX Facilities 27 Dragon Overview 29 Falcon 9 Overview 31 45th Space Wing Fact Sheet HIGH-RESOLUTION PHOTOS AND VIDEO SpaceX will post photos and video throughout the mission. High-Resolution photographs can be downloaded from: http://spacexlaunch.zenfolio.com Broadcast quality video can be downloaded from: https://vimeo.com/spacexlaunch/videos MORE RESOURCES ON THE WEB Mission updates will be posted to: For NASA coverage, visit: www.SpaceX.com http://www.nasa.gov/spacex www.twitter.com/elonmusk http://www.nasa.gov/nasatv www.twitter.com/spacex http://www.nasa.gov/station www.facebook.com/spacex www.youtube.com/spacex 1 WEBCAST INFORMATION The launch will be webcast live, with commentary from SpaceX corporate headquarters in Hawthorne, CA, at www.spacex.com. The webcast will begin approximately 40 minutes before launch. SpaceX hosts will provide information specific to the flight, an overview of the Falcon 9 rocket and Dragon spacecraft, and commentary on the launch and flight sequences. It will end when the Dragon spacecraft separates
    [Show full text]
  • Quality and Reliability: APL's Key to Mission Success
    W. L. EBERT AND E. J. HOFFMAN Quality and Reliability: APL’s Key to Mission Success Ward L. Ebert and Eric J. Hoffman APL’s Space Department has a long history of producing reliable spaceflight systems. Key to the success of these systems are the methods employed to ensure robust, failure-tolerant designs, to ensure a final product that faithfully embodies those designs, and to physically verify that launch and environmental stresses will indeed be well tolerated. These basic methods and practices have served well throughout the constantly changing scientific, engineering, and budgetary challenges of the first 40 years of the space age. The Space Department has demonstrated particular competence in addressing the country’s need for small exploratory missions that extend the envelope of technology. (Keywords: Quality assurance, Reliability, Spacecraft, Spaceflight.) INTRODUCTION The APL Space Department attempts to be at the and development is fundamentally an innovative en- high end of the quality and reliability scale for un- deavor, and any plan to carry out such work necessarily manned space missions. A track record of nearly 60 has steps with unknown outcomes. On the other hand, spacecraft and well over 100 instruments bears this out conventional management wisdom says that some de- as a success. Essentially, all of APL’s space missions are gree of risk and unpredictability exists in any major one-of-a-kind, so the challenge is to get it right the first undertaking, and the only element that differs in re- time, every time, by developing the necessary technol- search and development is the larger degree of risks.
    [Show full text]
  • Orion First Flight Test
    National Aeronautics and Space Administration orion First Flight Test NASAfacts Orion, NASA’s new spacecraft Exploration Flight Test-1 built to send humans farther During Orion’s flight test, the spacecraft will launch atop a Delta IV Heavy, a rocket built than ever before, is launching and operated by United Launch Alliance. While into space for the first time in this launch vehicle will allow Orion to reach an altitude high enough to meet the objectives for December 2014. this test, a much larger, human-rated rocket An uncrewed test flight called Exploration will be needed for the vast distances of future Flight Test-1 will test Orion systems critical to exploration missions. To meet that need, NASA crew safety, such as heat shield performance, is developing the Space Launch System, which separation events, avionics and software will give Orion the capability to carry astronauts performance, attitude control and guidance, farther into the solar system than ever before. parachute deployment and recovery operations. During the uncrewed flight, Orion will orbit The data gathered during the flight will influence the Earth twice, reaching an altitude of design decisions and validate existing computer approximately 3,600 miles – about 15 times models and innovative new approaches to space farther into space than the International Space systems development, as well as reduce overall Station orbits. Sending Orion to such a high mission risks and costs. altitude will allow the spacecraft to return to Earth at speeds near 20,000 mph. Returning
    [Show full text]
  • The "Bug" Heard 'Round the World
    ACM SIGSOFT SOFTWAREENGINEERING NOTES, Vol 6 No 5, October 1981 Page 3 THE "BUG" HEARD 'ROUND THE WORLD Discussion of the software problem which delayed the first Shuttle orbital flight JohnR. Garman Cn April 10, 1981, about 20 minutes prior to the scheduled launching of the first flight of America's Space Transportation System, astronauts and technicians attempted to initialize the software system which "backs-up" the quad-redundant primary software system ...... and could not. In fact, there was no possible way, it turns out, that the BFS (Backup Flight Control System) in the fifth onboard computer could have been initialized , Froperly with the PASS (Primary Avionics Software System) already executing in the other four computers. There was a "bug" - a very small, very improbable, very intricate, and very old mistake in the initialization logic of the PASS. It was the type of mistake that gives programmers and managers alike nightmares - and %heoreticians and analysts endless challenge. I% was the kind of mistake that "cannot happen" if one "follows all the rules" of good software design and implementation. It was the kind of mistake that can never be ruled out in the world of real systems development: a world involving hundreds of programmers and analysts, thousands of hours of testing and simulation, and millions of pages of design specifications, implementation schedules, and test plans and reports. Because in that world, software is in fact "soft" - in a large complex real time control system like the Shuttle's avionics system, software is pervasive and, in virtually every case, the last subsystem to stabilize.
    [Show full text]
  • Spacecraft & Vehicle Systems
    National Aeronautics and Space Administration Marshall Space Flight Center Spacecraft & Vehicle Systems Engineering Solutions for Space Science and Exploration Marshall’s Spacecraft and Vehicle Systems Department For over 50 years, the Marshall Space Flight Center has devel- for assessment of the orbiter’s thermal protection system prior oped the expertise and capabilities to successfully execute the to reentry and for debris anomaly resolution. In addition, the integrated design, development, test, and evaluation of NASA Natural Environments group supported the day-of -launch I-Load launch vehicles, and spacecraft and science programs. Marshall’s Updates, provided the mean bulk propellant temperature forecast Spacecraft and Vehicle Systems Department (EV) has been a prior to each Shuttle launch, and performed radiation assessments major technical and engineering arm to develop these vehicles of Shuttle avionics systems. Members in the department also and programs in the areas of Systems Engineering & Integration co-chaired several propulsion SE&I panels including panels for (SE&I), flight mechanics and analysis, and structural design and Aerodynamics, Thermal, and Loads disciplines. analysis. EV has performed advanced research and development for future spacecraft and launch vehicle systems, and has estab- EV provides design and analysis support to numerous Science and lished technical partnerships and collaborations with other NASA Mission Systems projects, including the Environmental Control & centers, the Department of Defense, the Department of Energy, Life Support System (ECLSS), the Microgravity Science Research industry, technical professional societies, and academia in order Rack, and the Node elements for the International Space Station. to enhance technical competencies and advanced technologies The department also developed and maintains the Chandra for future spacecraft and vehicle systems.
    [Show full text]
  • Nanoracks External Platform (NREP) Interface Definition Document (IDD)
    NanoRacks External Platform (NREP) Interface Definition Document (IDD) Doc No: NR-NREP-S0001 Revision: B © Copyright NanoRacks, LLC 2016. All Rights Reserved. NanoRacks External Platform IDD NREP Doc No: NR-NREP-S0001 Rev: B NanoRacks External Platform (NREP) IDD NREP Prepared by Steven Stenzel; Systems Engineer; Date Reviewed by Mark Rowley; Mechanical Design; Date Reviewed by Keith Tran; Operations Manager; Date Reviewed by Troy Guy; Avionics Manager; Date Reviewed by Bob Alexander; Safety; Date Reviewed by Susan Lufkin; Systems Engineer; Date Reviewed by Kirk Woellert; Payload Coordinator; Date Approved by Mike Lewis; Chief Technology Officer; Date NanoRacks External Platform IDD NREP Doc No: NR-NREP-S0001 Rev: B List of Revisions Revision Revision Date Revised By Revision Description - 3/16/2016 Steve Stenzel Initial Release A 4/20/2016 Steve Stenzel Update logo on cover page B 11/14/2016 C. Cummins Replace Proprietary Statement with a Copyright statement. NanoRacks External Platform IDD NREP Doc No: NR-NREP-S0001 Rev: B Table of Contents 1 Introduction 1 1.1 Purpose 1 1.2 Scope 1 1.3 Use 1 1.4 Exceptions 1 2 Acronyms, Definitions and Applicable Documents 2 3 NanoRacks NREP Overview 4 3.1 NREP Physical Descriptions 4 3.1.1 NREP-P Baseplate 4 3.1.2 NanoRacks External Plate - Payload 5 3.1.3 NREP Coordinate System 5 3.1.4 NREP General Dimensions 6 3.1.5 NREP Payload Configurations 6 3.1.6 NREP Baseplate Location Numbering System 7 3.2 NREP Operations Overview 10 3.2.1 Schedule 10 3.2.2 Ground Operations 11 3.2.2.1 Delivery to NanoRacks
    [Show full text]
  • The Space Race
    The Space Race Aims: To arrange the key events of the “Space Race” in chronological order. To decide which country won the Space Race. Space – the Final Frontier “Space” is everything Atmosphere that exists outside of our planet’s atmosphere. The atmosphere is the layer of Earth gas which surrounds our planet. Without it, none of us would be able to breathe! Space The sun is a star which is orbited (circled) by a system of planets. Earth is the third planet from the sun. There are nine planets in our solar system. How many of the other eight can you name? Neptune Saturn Mars Venus SUN Pluto Uranus Jupiter EARTH Mercury What has this got to do with the COLD WAR? Another element of the Cold War was the race to control the final frontier – outer space! Why do you think this would be so important? The Space Race was considered important because it showed the world which country had the best science, technology, and economic system. It would prove which country was the greatest of the superpowers, the USSR or the USA, and which political system was the best – communism or capitalism. https://www.youtube.com/watch?v=xvaEvCNZymo The Space Race – key events Discuss the following slides in your groups. For each slide, try to agree on: • which of the three options is correct • whether this was an achievement of the Soviet Union (USSR) or the Americans (USA). When did humans first send a satellite into orbit around the Earth? 1940s, 1950s or 1960s? Sputnik 1 was launched in October 1957.
    [Show full text]
  • The SKYLON Spaceplane
    The SKYLON Spaceplane Borg K.⇤ and Matula E.⇤ University of Colorado, Boulder, CO, 80309, USA This report outlines the major technical aspects of the SKYLON spaceplane as a final project for the ASEN 5053 class. The SKYLON spaceplane is designed as a single stage to orbit vehicle capable of lifting 15 mT to LEO from a 5.5 km runway and returning to land at the same location. It is powered by a unique engine design that combines an air- breathing and rocket mode into a single engine. This is achieved through the use of a novel lightweight heat exchanger that has been demonstrated on a reduced scale. The program has received funding from the UK government and ESA to build a full scale prototype of the engine as it’s next step. The project is technically feasible but will need to overcome some manufacturing issues and high start-up costs. This report is not intended for publication or commercial use. Nomenclature SSTO Single Stage To Orbit REL Reaction Engines Ltd UK United Kingdom LEO Low Earth Orbit SABRE Synergetic Air-Breathing Rocket Engine SOMA SKYLON Orbital Maneuvering Assembly HOTOL Horizontal Take-O↵and Landing NASP National Aerospace Program GT OW Gross Take-O↵Weight MECO Main Engine Cut-O↵ LACE Liquid Air Cooled Engine RCS Reaction Control System MLI Multi-Layer Insulation mT Tonne I. Introduction The SKYLON spaceplane is a single stage to orbit concept vehicle being developed by Reaction Engines Ltd in the United Kingdom. It is designed to take o↵and land on a runway delivering 15 mT of payload into LEO, in the current D-1 configuration.
    [Show full text]
  • Recommended Practices for Human Space Flight Occupant Safety
    Recommended Practices for Human Space Flight Occupant Safety Version 1.0 August 27, 2014 Federal Aviation Administration Office of Commercial Space Transportation 800 Independence Avenue, Room 331 7 3 Washington, DC 20591 0 0 - 4 1 C T Recommended Practices for Human Space Flight Page ii Occupant Safety – Version 1.0 Record of Revisions Version Description Date 1.0 Baseline version of document August 27, 2014 Recommended Practices for Human Space Flight Page iii Occupant Safety – Version 1.0 Recommended Practices for Human Space Flight Page iv Occupant Safety – Version 1.0 TABLE OF CONTENTS A. INTRODUCTION ............................................................................................................... 1 1.0 Purpose ............................................................................................................................. 1 2.0 Scope ................................................................................................................................ 1 3.0 Development Process ....................................................................................................... 2 4.0 Level of Risk and Level of Care ...................................................................................... 2 4.1 Level of Risk ................................................................................................................ 2 4.2 Level of Care ................................................................................................................ 3 5.0 Structure and Nature of the
    [Show full text]
  • An Assessment of Aerocapture and Applications to Future Missions
    Post-Exit Atmospheric Flight Cruise Approach An Assessment of Aerocapture and Applications to Future Missions February 13, 2016 National Aeronautics and Space Administration An Assessment of Aerocapture Jet Propulsion Laboratory California Institute of Technology Pasadena, California and Applications to Future Missions Jet Propulsion Laboratory, California Institute of Technology for Planetary Science Division Science Mission Directorate NASA Work Performed under the Planetary Science Program Support Task ©2016. All rights reserved. D-97058 February 13, 2016 Authors Thomas R. Spilker, Independent Consultant Mark Hofstadter Chester S. Borden, JPL/Caltech Jessie M. Kawata Mark Adler, JPL/Caltech Damon Landau Michelle M. Munk, LaRC Daniel T. Lyons Richard W. Powell, LaRC Kim R. Reh Robert D. Braun, GIT Randii R. Wessen Patricia M. Beauchamp, JPL/Caltech NASA Ames Research Center James A. Cutts, JPL/Caltech Parul Agrawal Paul F. Wercinski, ARC Helen H. Hwang and the A-Team Paul F. Wercinski NASA Langley Research Center F. McNeil Cheatwood A-Team Study Participants Jeffrey A. Herath Jet Propulsion Laboratory, Caltech Michelle M. Munk Mark Adler Richard W. Powell Nitin Arora Johnson Space Center Patricia M. Beauchamp Ronald R. Sostaric Chester S. Borden Independent Consultant James A. Cutts Thomas R. Spilker Gregory L. Davis Georgia Institute of Technology John O. Elliott Prof. Robert D. Braun – External Reviewer Jefferey L. Hall Engineering and Science Directorate JPL D-97058 Foreword Aerocapture has been proposed for several missions over the last couple of decades, and the technologies have matured over time. This study was initiated because the NASA Planetary Science Division (PSD) had not revisited Aerocapture technologies for about a decade and with the upcoming study to send a mission to Uranus/Neptune initiated by the PSD we needed to determine the status of the technologies and assess their readiness for such a mission.
    [Show full text]
  • Spacex CRS-4 National Aeronautics and Fourth Commercial Resupply Services Flight Space Administration
    SpaceX CRS-4 National Aeronautics and Fourth Commercial Resupply Services Flight Space Administration to the International Space Station September 2014 OVERVIEW The Dragon spacecraft will be filled with more than 5,000 pounds of supplies and payloads, including critical materials to support 255 science and research investigations that will occur during Expeditions 41 and 42. Dragon will carry three powered cargo payloads in its pressurized section and two in its unpressurized trunk. Science payloads will enable model organism research using rodents, fruit flies and plants. A special science payload is the ISS-Rapid Scatterometer to monitor ocean surface wind speed and direction. Several new technology demonstrations aboard will enable bone density studies, test how a small satellite moves and positions itself in space using new thruster technology, and use the first 3-D printer in space for additive manufacturing. The mission also delivers IMAX cameras for filming during four increments and replacement batteries for the spacesuits. After four weeks at the space station, the spacecraft will return with about 3,800 pounds of cargo, including crew supplies, hardware and computer resources, science experiments, space station hardware, and four powered payloads. DRAGON CARGO LAUNCH ITEMS RETURN ITEMS TOTAL CARGO: 4885 lbs / 2216 kg 3276 lbs / 1486 kg · Crew Supplies 1380 lbs / 626 kg 132 lbs / 60 kg Crew care packages Crew provisions Food · Vehicle Hardware 403 lbs / 183 kg 937 lbs / 425 kg Crew Health Care System hardware Environment Control & Life Support equipment Electrical Power System hardware Extravehicular Robotics equipment Flight Crew Equipment Japan Aerospace Exploration Agency equipment · Science Investigations 1644 lbs / 746 kg 2075 lbs / 941 kg U.S.
    [Show full text]
  • Magnetoshell Aerocapture: Advances Toward Concept Feasibility
    Magnetoshell Aerocapture: Advances Toward Concept Feasibility Charles L. Kelly A thesis submitted in partial fulfillment of the requirements for the degree of Master of Science in Aeronautics & Astronautics University of Washington 2018 Committee: Uri Shumlak, Chair Justin Little Program Authorized to Offer Degree: Aeronautics & Astronautics c Copyright 2018 Charles L. Kelly University of Washington Abstract Magnetoshell Aerocapture: Advances Toward Concept Feasibility Charles L. Kelly Chair of the Supervisory Committee: Professor Uri Shumlak Aeronautics & Astronautics Magnetoshell Aerocapture (MAC) is a novel technology that proposes to use drag on a dipole plasma in planetary atmospheres as an orbit insertion technique. It aims to augment the benefits of traditional aerocapture by trapping particles over a much larger area than physical structures can reach. This enables aerocapture at higher altitudes, greatly reducing the heat load and dynamic pressure on spacecraft surfaces. The technology is in its early stages of development, and has yet to demonstrate feasibility in an orbit-representative envi- ronment. The lack of a proof-of-concept stems mainly from the unavailability of large-scale, high-velocity test facilities that can accurately simulate the aerocapture environment. In this thesis, several avenues are identified that can bring MAC closer to a successful demonstration of concept feasibility. A custom orbit code that dynamically couples magnetoshell physics with trajectory prop- agation is developed and benchmarked. The code is used to simulate MAC maneuvers for a 60 ton payload at Mars and a 1 ton payload at Neptune, both proposed NASA mis- sions that are not possible with modern flight-ready technology. In both simulations, MAC successfully completes the maneuver and is shown to produce low dynamic pressures and continuously-variable drag characteristics.
    [Show full text]